Total air temperature probes for reducing deicing heater error

ABSTRACT

A total air temperature probe includes a probe head having an airflow inlet, a main airflow outlet, a main probe head wall extending from the airflow inlet to the main airflow outlet, and a flow separation bend wall positioned between the airflow inlet and the main airflow outlet. The flow separation bend wall is opposite the main probe head wall across a primary flow passage defined through the probe head from the airflow inlet to the main airflow outlet. A flow separation trip feature is defined on an interior surface of the main probe head wall for tripping a boundary layer flow separation in flow in the primary flow passage, e.g., for reduction of deicing heater error.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a divisional of U.S. patent application Ser. No.13/964,693 filed Aug. 12, 2013, which claims priority to U.S.Provisional Patent Application No. 61/684,714 filed Aug. 18, 2012, eachof which is incorporated by reference herein in its entirety.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present disclosure relates to total air temperature (TAT) probes orsensors. More particularly, the present disclosure relates to heated TATprobes.

2. Description of Related Art

Modem jet powered aircraft require very accurate measurement of outsideair temperature (OAT) for inputs to the air data computer, engine thrustmanagement computer, and other airborne systems. For these aircrafttypes, their associated flight conditions, and the use of total airtemperature probes in general, air temperature is better defined by thefollowing four temperatures: (1) Static air temperature (SAT) or(T_(S)), (2) total air temperature (TAT) or (T_(t)), (3) recoverytemperature (T_(r)), and (4) measured temperature (T_(m)). Static airtemperature (SAT) or (T_(S)) is the temperature of the undisturbed airthrough which the aircraft is about to fly. Total air temperature (TAT)or (T_(v)) is the maximum air temperature that can be attained by 100%conversion of the kinetic energy of the flight. The measurement of TATis derived from the recovery temperature (T_(r)), which is the adiabaticvalue of local air temperature on each portion of the aircraft surfacedue to incomplete recovery of the kinetic energy. Recovery temperature(T_(r)) is obtained from the measured temperature (T_(m)), which is theactual temperature as measured, and which differs from recoverytemperature because of heat transfer effects due to imposedenvironments.

Conventional TAT probes, although often remarkably efficient as TATsensors, sometimes face the difficulty of working in icing conditions.During flight in icing conditions, water droplets, and/or ice crystals,are ingested into the TAT probe where, under moderate to severeconditions, they can accrete around the opening of the internal sensingelement. An ice ridge can grow and eventually break free—clogging thesensor temporarily and causing an error in the TAT reading. To addressthis problem, conventional TAT probes have incorporated an elbow, orbend, to inertially separate these particles from the airflow beforethey reach the sensing element.

Another phenomenon which presents difficulties to some conventional TATprobe designs has to do with the problem of boundary layer separation,or “spillage,” at low mass flows. Flow separation creates two problemsfor the accurate measurement of TAT. The first has to do with turbulenceand the creation of irrecoverable losses that reduce the measured valueof TAT. The second is tied to the necessity of having to heat the probein order to prevent ice formation during icing conditions. Anti-icingperformance is facilitated by heater elements embedded in the housingwalls. Unfortunately, external heating also heats the internal boundarylayers of air which, if not properly controlled, provides an extraneousheat source in the measurement of TAT. This type of error, commonlyreferred to as deicing heater error (DHE), is difficult to correct for.Commonly, in TAT probes, the inertial flow separation bend describedabove has vent or bleed holes distributed along its inner surface. Theholes are vented, through a bleed port air exit, to a pressure equal toroughly that of the static atmospheric pressure outside of the TATprobe. In this manner, a favorable pressure difference is created whichremoves a portion of the boundary layer through the bleed holes, andpins the remaining boundary layer against the elbow's inner wall.

In certain situations, the differential pressure across the bleed holescan drop to zero due to the higher flow velocity along the elbow's innerradius. This stagnation of flow through the bleed holes creates a lossin boundary layer control. The resulting perturbation, if large enough,can cause the boundary layer to separate from the inner surface and makecontact with the sensing element. Because the housing walls are heated,so is the boundary layer. Hence, any contamination of the main airflowby the heated boundary layer will result in a corresponding error in theTAT measurement. In general, it is difficult to prevent the stagnationof some of the bleed holes. Thus, DHE is difficult to prevent or reduce.

Some solutions for these challenges have been described in U.S. Pat. No.7,357,572, U.S. Pat. No. 8,104,955, and U.S. Pat. No. 7,828,477, each ofwhich is incorporated by reference herein in its entirety. Suchconventional methods and systems have generally been consideredsatisfactory for their intended purpose. However, there is an everpresent need in the art for improved DHE performance. There also remainsa need in the art for such a systems and methods that are easy to makeand use. The present disclosure provides a solution for these problems.

SUMMARY OF THE INVENTION

A total air temperature probe includes a probe head having an airflowinlet, a main airflow outlet, a main probe head wall extending from theairflow inlet to the main airflow outlet, and a flow separation bendwall positioned between the airflow inlet and the main airflow outlet.The flow separation bend wall is opposite the main probe head wallacross a primary flow passage defined through the probe head from theairflow inlet to the main airflow outlet. A flow separation trip featureis defined on an interior surface of the main probe head wall fortripping a boundary layer flow separation in flow in the primary flowpassage.

In certain embodiments, a strut connects between the probe head and anopposed probe mount. The strut defines a sensor passage connected to theprimary flow passage and oriented at an angle relative to a flow axisdefined from the airflow inlet to the main airflow outlet. A temperaturesensor is mounted within the sensor passage for total air temperaturemeasurements. A deicing heater is operatively connected to heat theprobe head and to form a heated boundary layer within the primary flowpassage with a portion of the heated boundary layer passing from theprimary flow passage into the sensor passage. The sensor and the flowseparation trip feature are positioned so the portion of the heatedboundary layer passing into the sensor passage substantially avoids thesensor for reduction of deicing heater error. It is also contemplatedthat a thermal shield can be included in the sensor passage between thesensor and the sensor passage interior wall, wherein the flow separationtrip feature and thermal shield are positioned so the portion of theheated boundary layer passing into the sensor passage substantiallyavoids spilling into the thermal shield.

It is contemplated that in certain embodiments, the flow separation tripfeature includes a notch set in from the interior surface of the mainprobe head wall. The notch can span the main probe head wall from one ofa pair of the opposed sidewalls to the other, wherein each sidewallconnects between the main probe head wall and the flow separation bendwall. The notch can have a leading notch edge spaced inward from theairflow inlet by 0.8 inches (2.032 cm), and can have a depth relative tothe interior surface of the main probe head wall of 0.008 inches (0.0203cm).

It is also contemplated that in certain embodiments, the flow separationtrip feature includes a protrusion set out from the interior surface ofthe main probe head wall. The protrusion can span the main probe headwall from one of the opposed sidewalls to the other as described above.The protrusion can have a leading edge spaced inward from the airflowinlet by 0.8 inches (2.032 cm), and can protrude from the interiorsurface of the main probe head wall by 0.008 inches (0.0203 cm).

These and other features of the systems and methods of the subjectdisclosure will become more readily apparent to those skilled in the artfrom the following detailed description of the preferred embodimentstaken in conjunction with the drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

So that those skilled in the art to which the subject disclosureappertains will readily understand how to make and use the devices andmethods of the subject disclosure without undue experimentation,preferred embodiments thereof will be described in detail herein belowwith reference to certain figures, wherein:

FIG. 1 is a perspective view of an exemplary embodiment of a total airtemperature probe constructed in accordance with the present disclosure,showing the probe head, strut, and probe mount;

FIG. 2 is a side elevation view of the total air temperature probe ofFIG. 1, showing the airflow inlet and main airflow outlet of the primaryflow passage through the probe head;

FIG. 3 is an inlet end elevation view of a portion of the total airtemperature probe of FIG. 1, showing the flow separation trip featurespanning from sidewall to sidewall in the probe head;

FIG. 4 is cross-sectional side elevation view of a portion of the totalair temperature probe of FIG. 1, schematically showing how the heatedboundary layer avoids contacting the sensor;

FIG. 5 is a cross-sectional side elevation view of a portion of thetotal air temperature probe of FIG. 1, showing the separation tripfeature as a notch set into the inner surface of the main probe headwall; and

FIG. 6 is a cross-sectional side elevation view of a portion of thetotal air temperature probe of FIG. 1, showing another exemplaryembodiment of the separation trip feature as a protrusion protrudingfrom the inner surface of the main probe head wall.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

Reference will now be made to the drawings wherein like referencenumerals identify similar structural features or aspects of the subjectdisclosure. For purposes of explanation and illustration, and notlimitation, a partial view of an exemplary embodiment of a total airtemperature probe in accordance with the disclosure is shown in FIG. 1and is designated generally by reference character 100. Otherembodiments of total air temperature probes in accordance with thedisclosure, or aspects thereof, are provided in FIGS. 2-6, as will bedescribed. The systems and methods described herein can be used toreduce or eliminate deicing heater error (DHE) in total air temperature(TAT) probes.

Total air temperature probe 100 includes a probe head 102 having anairflow inlet 110, a main airflow outlet 112 (shown in FIG. 2), and astrut 104 connecting between probe head 102 and an opposed probe mount106. A main probe head wall 108 extends from inlet 110 to outlet 112.Cross-ports 114 are defined in each respective sidewall 116 of probehead 102.

Referring now to FIGS. 3 and 4, a flow separation bend wall 118 ispositioned between inlet 110 and outlet 112. Flow separation bend wall118 is opposite main probe head wall 108 across a primary flow passage120 that is defined through probe head 102 from inlet 110 to mainairflow outlet 112. Each sidewall 116 connects between main probe headwall 108 and flow separation bend wall 118.

A flow separation trip feature 122 is defined on an interior surface ofthe main probe head wall 108 for tripping a boundary layer flowseparation in flow in primary flow passage 120. In each of FIGS. 3 and4, trip feature 122 is shown schematically.

Strut 104 defines a sensor passage 124 that is fluidly connected toprimary flow passage 120. Sensor passage 124 is oriented at an obliqueangle relative to a flow axis A defined from inlet 110 to main airflowoutlet 112, however those skilled in the art will readily appreciatethat a 90° angle can also be used as suitable for given applications.

A temperature sensor 126 is mounted within sensor passage 124 for totalair temperature measurements. A deicing heater is imbedded in main probehead wall 108, flow separation bend wall 118, and sidewalls 116positioned between inlet 110 and outlet 112, as well as in strut 104,and is operatively connected to heat probe head 102 and strut 104 and toform a heated boundary layer 130 within the primary flow passage with aportion 132 of the heated boundary layer passing from primary flowpassage 120 into the sensor passage 124. Boundary layer 130 is indicatedschematically by arrows in FIG. 4. Sensor 126 and trip feature 122 arepositioned so portion 132 of the heated boundary layer 130 passing intosensor passage 124 substantially avoids sensor 126 for reduction ofdeicing heater error. Sensor 126 and trip feature 122 are alsopositioned so a heated boundary layer 133 from the aft wall of passage124 substantially avoids sensor 126. A thermal shield 134 is included insensor passage 124 between sensor 126 and the sensor passage interiorwall. Trip feature 122 and thermal shield 134 are positioned so theportion 132 of the heated boundary layer 130 as well as boundary layer133 passing into sensor passage 124 substantially avoid spilling intothermal shield 134. Since little or no portion of heated boundary layers130 and 133 enters thermal shield 134 or contacts sensor 126, deicingheater error (DHE) is reduced or eliminated.

Flow separation trip feature 122 is a notch set in from the interiorsurface of main probe head wall 108. As indicated schematically in FIG.3, the notch spans main probe head wall 108 from one sidewall 116 to theother. Referring to FIG. 5, the notch can have a leading notch edgespaced inward from inlet 110 by a length l of 0.8 inches (2.032 cm), andcan have a depth d relative to the interior surface of main probe headwall 108 of 0.008 inches (0.0203 cm). Referring to FIG. 6, it is alsocontemplated that the flow separation trip feature can instead be aprotrusion 222 set out from the interior surface of main probe head wall108. Protrusion 222 can span main probe head wall 108 from one sidewall116 to the other as described above. Protrusion 222 can be formedintegral with probe head 102, or can be formed separately and joined oradhered to the inner surface of main probe head wall 108. Protrusion 222can have a leading edge spaced inward from inlet 110 by a length l of0.8 inches (2.032 cm), and can protrude from the interior surface ofmain probe head wall 108 by a thickness d of 0.008 inches (0.0203 cm).Protrusion 222 also has a width w of 0.125 inches (0.318 cm).

Potential advantages of probes in accordance with the present disclosureinclude more uniform and consistent airflow over the sensing elements,for example at conditions with low Zeta values where Zeta is defined ascorrected Mach number for a particular altitude (e.g., at high Machnumbers and at high altitudes, such as over 40,000 ft (12,192 m) andover Mach 0.77). This means a given TAT probe will have more consistentreadings, as well as readings being more consistent from one TAT probeto another. Another potential advantage is reduced sensitivity toboundary layer separation. Reduction of deicing heater error (DHE),e.g., at high altitudes, can advantageously reduce the number of totalair temperature (TAT) probe miscompares in systems with multiple TATprobes, without negatively effecting TAT probe performance at loweraltitudes, e.g., at or near sea level.

The methods and systems of the present disclosure, as described aboveand shown in the drawings, provide for total air temperature (TAT)probes with superior properties including reduced or eliminated deicingheater error (DHE). While the apparatus and methods of the subjectdisclosure have been shown and described with reference to preferredembodiments, those skilled in the art will readily appreciate thatchanges and/or modifications may be made thereto without departing fromthe spirit and scope of the subject disclosure.

What is claimed is:
 1. A total air temperature probe comprising: a probehead having an airflow inlet, a main airflow outlet, a main probe headwall extending from the airflow inlet to the main airflow outlet, and aflow separation bend wall positioned between the airflow inlet and themain airflow outlet, the flow separation bend wall being opposite themain probe head wall across a primary flow passage defined through theprobe head from the airflow inlet to the main airflow outlet; a flowseparation trip feature defined on an interior surface of the main probehead wall for tripping a boundary layer flow separation in flow in theprimary flow passage; a strut connecting between the probe head and anopposed probe mount, the strut defining a sensor passage connected tothe primary flow passage and oriented at an angle relative to a flowaxis defined from the airflow inlet to the main airflow outlet, whereina temperature sensor is mounted within the sensor passage for total airtemperature measurements; a thermal shield is included in the sensorpassage between the sensor and an interior wall of the sensor passage;and a deicing heater operatively connected to heat the probe head andstrut to form a heated boundary layer within the primary flow passagewith a portion of the heated boundary layer passing from the primaryflow passage into the sensor passage, wherein the flow separation tripfeature is positioned so the portion of the heated boundary layerpassing into the sensor passage substantially avoids spilling into thethermal shield for reduction of deicing heater error.
 2. A total airtemperature probe as recited in claim 1, wherein the flow separationtrip feature includes a notch set in from the interior surface of themain probe head wall.
 3. A total air temperature probe as recited inclaim 2, wherein the notch has a leading notch edge spaced inward fromthe airflow inlet by 0.8 inches (2.032 cm).
 4. A total air temperatureprobe as recited in claim 2, wherein the notch has a depth relative tothe interior surface of the main probe head wall of 0.008 inches (0.0203cm).
 5. A total air temperature probe as recited in claim 1, wherein theflow separation trip feature includes a protrusion set out from theinterior surface of the main probe head wall.
 6. A total air temperatureprobe as recited in claim 5, wherein the protrusion has a leading edgespaced inward from the airflow inlet by 0.8 inches (2.032 cm).
 7. Atotal air temperature probe as recited in claim 5, wherein theprotrusion protrudes from the interior surface of the main probe headwall by 0.008 inches (0.0203 cm).
 8. A total air temperature probecomprising: a probe head having an airflow inlet, a main airflow outlet,a main probe head wall extending from the airflow inlet to the mainairflow outlet, and a flow separation bend wall positioned between theairflow inlet and the main airflow outlet, the flow separation bend wallbeing opposite the main probe head wall across a primary flow passagedefined through the probe head from the airflow inlet to the mainairflow outlet; opposed sidewalls, each sidewall connecting between themain probe head wall and the flow separation bend wall; a flowseparation trip feature defined on an interior surface of the main probehead wall for tripping a boundary layer flow separation in flow in theprimary flow passage, wherein the flow separation trip feature spans themain probe head wall from one of the opposed sidewalls to the other, andwherein the flow separation trip feature has a leading edge spacedinward from the airflow inlet; a strut connecting between the probe headand an opposed probe mount, the strut defining a sensor passageconnected to the primary flow passage and oriented at an angle relativeto a flow axis defined from the airflow inlet to the main airflowoutlet, wherein a temperature sensor is mounted within the sensorpassage for total air temperature measurements; a thermal shield isincluded in the sensor passage between the sensor and an interior wallof the sensor passage; and a deicing heater operatively connected toheat the probe head and strut to form a heated boundary layer within theprimary flow passage with a portion of the heated boundary layer passingfrom the primary flow passage into the sensor passage, wherein the flowseparation trip feature is positioned so the portion of the heatedboundary layer passing into the sensor passage substantially avoidsspilling into the thermal shield for reduction of deicing heater error.9. A total air temperature probe as recited in claim 8, wherein the flowseparation trip feature includes a notch set in from the interiorsurface of the main probe head wall.
 10. A total air temperature probeas recited in claim 9, wherein the notch has a leading notch edge spacedinward from the airflow inlet by 0.8 inches (2.032 cm).
 11. A total airtemperature probe as recited in claim 9, wherein the notch has a depthrelative to the interior surface of the main probe head wall of 0.008inches (0.0203 cm).
 12. A total air temperature probe as recited inclaim 8, wherein the flow separation trip feature includes a protrusionset out from the interior surface of the main probe head wall.
 13. Atotal air temperature probe as recited in claim 12, wherein theprotrusion has a leading edge spaced inward from the airflow inlet by0.8 inches (2.032 cm).
 14. A total air temperature probe as recited inclaim 12, wherein the protrusion protrudes from the interior surface ofthe main probe head wall by 0.008 inches (0.0203 cm).